[특허]Dual-stage gas generator utilizing eco-friendly gas generant formulation for military applications

Textron Systems Corporation

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Dual-stage gas generator utilizing eco-friendly gas generant formulation for military applications

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F42C-019/08
미국특허분류(USC)	102/202; 102/380; 280/741; 149/109.2
출원번호	US-0242742 (2002-09-12)
발명자 / 주소	Daoud, Sami
출원인 / 주소	Textron Systems Corporation
대리인 / 주소	McDermott Will &
인용정보	피인용 횟수 : 4 인용 특허 : 25

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This invention relates to a gas generator having two or more compartments, each with a separate initiator, with one compartment discharging before another, i.e., the compartments discharge sequentially. Each compartment has the same propellants, but the propellants have different geometries in each compartment, which results in different rates of gas evolution from each compartment. The gas generator has a rapid initial inflation, followed by a more gradual inflation rate in the subsequent stages, improving safety to occupants. One propellant used for the gas generator comprises (1) ammonium nitrate as the oxidizer, (2) a fuel such as CL-20. and (3) a binder such as polycaprolactone. A second propellant comprises by weight approximately 70-95% energetic nitrate fuel, 5-25% energetic polymer binder and 0.1-5% flash suppressant. No hot metal particles (e.g., CuO) are generated in the new systems.

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1. A gas generator for military applications comprising at least first and second adjacent gas generation compartments, each being capable of discharging gas therefrom at a different time and different volumetric rate, wherein each compartment contains the same propellant and an initiator, further wherein the propellant has a different geometry in each compartment which results in different rates of gas evolution from each compartment upon initiation such that the ratio of gas generation in the first compartment to that in the second compartment is greater than one; and also wherein said propellant consists essentially of on a weight basis approximately (a) 84-95% of phase-stabilized ammonium nitrate as an oxidizer, (b) 3.4-13.4% of a fuel selected from the group consisting of hexanitrohexaazaisowurtzitane (CL-20), cyclotrimethylenetribitramine (RDX), cyclotetramethylene-tetranitramine (HMX), nitroguanidine (NGU), tri-amino-trinitro-benzene (TATB), 2,6-diamino-3,5-dinitropyrazine-1-oxide (LLM-105), ethylene dinitramine (EDNA), and mixtures thereof, and (c) 1.5-2.6% of a binder selected from the group consisting of polycaprolactone (PCL), polyisobutylene (PIB), and polyvinylpyrrolidone, and mixtures thereof, wherein the products of combustion of said propellant are non-toxic gases and are non-metallic.2. A gas generator according to claim 1 wherein the change of pressure as a function of time from the first of said compartments is at least 2 times greater than the change of pressure as a function of time from the second of said compartments.3. A gas generator according to claim 1 wherein the products of combustion of said propellant consist of water, nitrogen and CO2.4. A gas generator according to claim 1 wherein said propellant is made bya. preparing a mixture of the components of said propellant in wet or dry form, b. forming said mixture into tablets, disks or granules, c. if wet, allowing said tablets, disks or granules to dry, and d. perforating said tablets, disks or granules to achieve the desired geometry. 5. A gas generator according to claim 1 wherein said propellant has density greater than or equal to approximately 92% of theoretical density.6. A gas generator for military applications comprising at least two chambers, each said chamber being capable of discharging gas therefrom at a different time and different volumetric rate, each said chamber containing the same propellant and an initiator, wherein said propellant comprises on a weight basis approximately (a) 84-95% of an oxidizer, (b) 3.4-13.4% of a fuel, and (c) 1.5-2.6% of a binder, wherein the products of combustion of said propellant are non-toxic gases and are non-metallic, further wherein said oxidizer is ammonium nitrate, said fuel is hexanitrohexaazaisowurtzitane (CL-20), and said binder is polycaprolactone (PCL).7. The gas generator of claim 6, wherein said propellant comprises by weight approximately 89.5% ammonium nitrate, approximately 8.4% hexanitrohexaazaisowurtzitane (CL-20), and approximately 2.1% polycaprolactone (PCL).8. A process for controlling the rate of inflation of an airbag used in military applications, comprising the following sequential steps:a. connecting to said airbag a gas generator comprising at least first and second adjacent gas generation compartments, each being capable of discharging gas therefrom at a different time and different volumetric rate, wherein each compartment contains the same propellant and an initiator, further wherein the propellant has a different geometry in each compartment which results in different rates of gas evolution from each compartment upon initiation such that the ratio of gas generation in the first compartment to that in the second compartment is greater than one; and also wherein said propellant consists essentially of on a weight basis approximately (a) 84-95% of phase-stabilized ammonium nitrate as an oxidizer, (b) 3.4-13.4% of a fuel selected from the group consisting of hexanitrohexaazaisowurtzitane (CL-20), cyclotrimethylenetribitramine (RDX), cyclotetramethylene-tetranitramine (HMX), nitroguanidine (NGU), tri-amino-trinitro-benzene (TATB), 2,6-diamino-3,5 -dinitropyrazine-1-oxide (LLM-105), ethylene dinitramine (EDNA), and mixtures thereof, and (c) 1.5-2.6% of a binder selected from the group consisting of polycaprolactone (PCL), polyisobutylene (PIB), and polyvinylpyrrolidone, and mixtures thereof, wherein the products of combustion of said propellant non-toxic gases and are non-metallic, b. causing each of said compartments to discharge at a different, predetermined time, and c causing the effluent of each of said compartments to flow into said airbag. 9. A process according to claim 8 wherein said oxidizer is ammonium nitrate, said fuel is hexanitrohexaazaisowurtzitane (CL-2), and said binder is polycaprolactone (PCL).10. A process according to claim 8 wherein said propellant comprises by weight approximately 89.5% ammonium nitrate, approximately 8.4% hexanitrohexaazaisowurtzitane (CL-20), and approximately 2.1% polycaprolactone (PCL).11. A process according to claim 8 wherein the change of pressure as a function of time from the first of said compartments is at least 2 times greater than the change of pressure as a function of time from the second of said compartments.12. A process according to claim 8 wherein the products of combustion of said propellant consist of water, nitrogen and CO2.13. A process according to claim 8 wherein said propellant is made bya. preparing a mixture of the components of said propellant in wet or dry form, b. forming said mixture into tablets, disks or granules, c. if wet, allowing said tablets, disks or granules to dry, and d. perforating said tablets, disks or granules to achieve the desired geometry. 14. A process according to claim 8 wherein said propellant has density greater than or equal to approximately 92% of theoretical density.

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Dual-stage gas generator utilizing eco-friendly gas generant formulation for military applications

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